Flight control method

A technology of flight control and aircraft, applied in the fields of flight control and aircraft design, can solve the problems of pilots being unable to effectively control the aircraft, increased aerodynamic resistance, increased fuel consumption, etc., and achieve the effects of saving fuel, overcoming resistance and reducing resistance

Inactive Publication Date: 2012-08-22
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Abstract
  • Description
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Problems solved by technology

[0010] Purpose of the present invention: to solve the problem that the pilot cannot effectively control the aircraft by using the existing flight control method in the case of failure, failure, or damage of the actuator and the aerodynamic surface, so that the aircraft can still fly normally and safely under these special circumstances, and at the same time solve the problem of The problem of increased aerodynamic resistance and increased fuel consumption when the existing flight control method uses the aerodynamic surface to control the aircraft

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Embodiment Construction

[0024] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0025] In the case of failure of the traditional aerodynamic surface or actuator of the aircraft, the pitch and roll control of the aircraft can be realized by applying the following method involved in the present invention, and the specific principles are as follows:

[0026] The operating principle of the head-up action of the pitch channel is as follows: figure 1 As shown, several fuel circuits 1 parallel to the symmetry plane of the aircraft are designed in the aircraft wing and fuselage fuel tanks, and the fuel flows in these "fuel circuits 1" at a certain speed and direction 3 through the oil pump, so as to realize the Positive pitch maneuver.

[0027] When the aircraft is flying in the trim state, the sum of the external forces is basically equal to zero. According to the principle of momentum moment conservation, when the fuel in these fuel circuits ...

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Abstract

The invention relates to the field of the design of aircrafts, in particular to a flight control method. According to the flight control method, through designing special fuel loops in an aircraft body structure, fuel can flow in the loops according to specified direction and speed, and thus, the aim of controlling the motion of an aircraft is reached. The method can be independently applied to an aircraft and can also be used through being combined with other flight control methods. With the adoption of the method, the defects that the control redundancy is insufficient, the aircraft is out of control in case of battle damage and failure, the specific fuel consumption is large, and the like, of the traditional control method are overcome.

Description

technical field [0001] The invention relates to the field of aircraft design, in particular to the field of flight control. Background technique [0002] At present, the control of the aircraft at home and abroad is realized by the pilot operating the mechanical actuator through the flight control system, and the mechanical actuator drives the aerodynamic surface of the aircraft. At present, the aircraft mainly controls the flight trajectory through the change of attitude, and for civil aircraft, all of them adopt this form. The aerodynamic surfaces capable of generating aircraft motions such as pitch and roll are deflected by at least one mechanical actuator, typically driven by hydraulic or electric steering gear. [0003] In consideration of flight safety, the power unit of the mechanical actuator generally needs to be backed up. The backup power unit must ensure that it can quickly and effectively replace the failed power unit in case of failure. However, the backup h...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D31/00B64D37/32
Inventor 仇江高亚奎安刚林皓黑文静
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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